Detergent delivery methods and systems for turbine engines

ABSTRACT

Methods and systems for in situ cleaning of internal cooling circuits of a turbine engine with detergent that provide cleaning a turbine engine that includes circumferentially arranged internal impingement cooling circuits that each include a baffle plate configured to air cool a respective surface or component of the turbine engine. Detergent is introduced through the outer wall and proximate to a back side of a baffle plate such that the detergent passes through at least aperture in the baffle plate and acts at least upon the surface or component that the baffle plate is configured to cool. The detergent may also act on the front side of the baffle plate that is proximate to the surface or component.

The present application is a divisional application of U.S. Ser. No.14/621,465 filed on Feb. 13, 2015.

The present application relates generally to methods and system forinternal cleaning of turbine engines, and more particularly to methodsand system of cleaning internal cooling circuits of turbine engines withdetergent.

Turbines, such as gas turbine engines, typically include internalcooling passages that are designed to impingement cool one or morecomponents during use. For example, the high pressure section of a gasturbine engine typically includes numerous circumferentially-arrangedimpingement internal cooling circuits that allow for higher temperaturesin the turbine. Unfortunately, impingement internal cooling circuits ofturbine engines tend to become partially or completely blocked withparticulate matter that reduces the cooling efficiency of the circuits.For example, particulate matter may enter a turbine engine duringservice or during use, such as during environmental events such as duststorms. The particulate matter may be fine scale (e.g., less than 10microns) dust, debris or other pollutants (reacted or non-reacted). Inaddition to blocking or clogging the cooling circuits, the particulatematter may also become deposited on cooled components and create aninsulating layer between the surface of the component and the coolingmedium of the cooling circuits. The reduced cooling efficiency createdby the at least partially blocked cooling circuits and the insulatinglayers on the cooled components can increase the operating temperatureand reduce the life of the components. In addition, the particulatematter that is entrained in the air that enters the turbine engine andtravels within the cooling circuits can contain sulphur-containingspecies which can corrode components of the turbine.

Unfortunately, internal cooling passages that are designed to cool oneor more components of gas turbine engines are typically either notcleaned or cleaned through expensive, time consuming, labor intensiveand/or ineffective means. For example, turbine engines may be removedfrom service (e.g., detached from the aircraft, power plant or othermachine that the engine powers or is otherwise used with) andsubstantially dismantled to provide direct access to the internalcooling passages for cleaning. In this way, traditionally, if cleaned,the circumferentially arranged cooling circuits are cleaned individuallyand not in situ.

SUMMARY OF THE INVENTION

It is therefore highly desirable to be able to clean the internalcooling circuits of gas turbine engines to remove the particulate matterthat can accumulate. For example, cleaning the internal cooling circuitsof a gas turbine engine to return the cooling efficiency of the circuitsto their original condition before entry into service, or close thereto,is substantially beneficial. It is also highly desirable to achieve acleaning operation that is capable of cleaning all of thecircumferentially arranged internal cooling circuit system within theengine. As many gas turbine engines are utilized by aircraft, it isnecessary that the cleaning operation used for removal of particulatematter that has become accreted within cooling circuits be compliantwith all Federal Aviation Administration (FAA) and other travel oraviation regulations. Still further, a cleaning operation that isperformed while the gas turbine is in its installed state (such as anaircraft engine installed on the aircraft or a power generating gasturbine installed in a power plant), or at least without substantialdisassembly, is needed.

In one aspect, the present disclosure provides a method of cleaning aturbine engine that includes at least one internal impingement coolingcircuit with a baffle plate configured to air cool a component of theturbine engine. The method includes introducing detergent to a back sideof a baffle plate of the turbine engine such that the detergent passesthrough at least one aperture in the baffle plate and acts at least uponthe component that the baffle plate is configured to air impingementcool to clean matter from the component.

Introducing detergent to a back side of a baffle plate of the turbineengine may comprise introducing detergent into a pre-baffle cavitypositioned proximate to the back side of the baffle plate. The methodmay further include accessing the back side of the baffle plate of theturbine engine through a port in an outer wall of the turbine engine.The port in the outer wall of the turbine engine may provide apassageway to an internal cooling air channel of a respective internalimpingement cooling circuit that feeds the baffle plate with air to aircool the component. The port may be an aperture in an outer case of theturbine engine configured to house a fuel line coupled to a fuel nozzle.Accessing a back side of a baffle plate of the turbine engine through aport in an outer wall of the turbine engine may include positioning adetergent delivery mechanism through the port and proximate to the backside of the baffle plate.

The impingement-cooled component may be a shroud coupled to a shroudhanger positioned at least partially on the back side of the shroud. Thedetergent may be passed through at least one aperture in the hanger andmay be introduced into a pre-baffle cavity between the hanger and theback side of the shroud.

The detergent may act on a front side of the baffle plate thatsubstantially faces the component that the baffle plate is configured toair impingement cool. The detergent may include an acidic, water-basedreagent including an organic surfactant and a corrosion inhibitordesigned to selectively dissolve at least one of sulfate, chloride andcarbonate based species while being substantially unreactive with thematerial forming the component. The turbine engine may be attached to anaircraft. The internal impingement cooling circuits may include aplurality of circumferentially arranged cooling circuits each includinga baffle plate configured to cool a respective one of circumferentiallyarranged components. The method may include substantially simultaneouslyintroducing detergent to the back side of a plurality of thecircumferentially arranged baffle plates such that the detergent passesthrough apertures in the baffle plates and acts at least upon therespective circumferentially arranged components that the baffle platesare configured to air cool. The cleaning method may include introducingdetergent to a back side of a baffle plate of the turbine engine suchthat the detergent passes through a plurality of apertures in the baffleplate to form a plurality of discrete jets of detergent that act atleast upon the component that the baffle plate is configured to airimpingement cool to clean matter from the component.

In another aspect, the present disclosure provides a method of cleaninga turbine engine. The method includes obtaining a turbine engineincluding circumferentially arranged internal impingement coolingcircuits each with a baffle plate configured to air impingement cool arespective circumferentially arranged component of the turbine engine,wherein the baffle plates each include a back side, a front sidepositioned proximate to the respective component, and at least oneaperture extending from the front side to the back side. The methodfurther includes positioning a detergent delivery mechanism through atleast one access aperture in the outer wall of the turbine and proximateto the back side of the baffle plates. The method also includesintroducing detergent to the back side of the baffle plates via thedetergent delivery mechanism such that the detergent passes through theat least one aperture in the baffle plates and acts upon the componentsand the front sides of the baffle plates to clean matter therefrom.

The components may be circumferentially arranged shrouds each coupled toa shroud hanger positioned at least partially on the back side of theshrouds, and the method may include passing the detergent through anaperture in each of the hangers and into a pre-baffle cavity formedbetween the hangers and the back sides of the baffle plates. Theaperture in each of the hangers may be in communication with therespective internal cooling passageway of the respectivecircumferentially arranged internal impingement cooling circuit to feedair to the respective baffle plate to air cool the respective component.

The turbine engine may be attached to an aircraft. The detergent mayinclude an acidic, water-based reagent including an organic surfactantand a corrosion inhibitor designed to selectively dissolve at least oneof sulfate, chloride and carbonate based species while beingsubstantially unreactive with the material forming the components.

In another aspect, the present disclosure provides a system for cleaninga turbine engine that includes at least one internal impingement coolingcircuit with an internal cooling passageway in communication with abaffle plate that is configured to air cool a component of the turbineengine. The system includes a detergent delivery mechanism extendingthrough an opening in the outer wall of the turbine and proximate to aback side of the baffle plate. The system further includes a source ofdetergent including an acidic, water-based reagent with an organicsurfactant and a corrosion inhibitor in fluid communication with thedetergent delivery mechanism.

The component may be a shroud coupled to a shroud hanger positioned atleast partially on the back side of the shroud, and the detergentdelivery mechanism may extend to an aperture in the shroud hanger todeliver the detergent into a pre-baffle cavity that is formed betweenthe shroud hanger and the back side of the baffle plate. The detergentdelivery mechanism may extend to a pre-baffle cavity that is proximateto a back side of the baffle plate. The source of a detergent includingan acidic, water-based reagent may be configured to deliver thedetergent to the back side of the baffle via the detergent deliverymechanism such that the delivered detergent passes through apertures inthe baffle plate and acts upon the component and a front side of thebaffle plate to clean matter from therefrom.

These and other objects, features and advantages of this disclosure willbecome apparent from the following detailed description of the variousaspects of the disclosure taken in conjunction with the accompanyingdrawings.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a cross-sectional view of an exemplary internal impingementcooling circuit for a shroud of an exemplary turbine engine;

FIG. 2 is an enlarged cross-sectional view of a portion of the baffleplate portion of the exemplary internal impingement cooling circuit ofFIG. 1;

FIG. 3 illustrates a graphical representation of an exemplarycircumferential arrangement of internal impingement cooling circuits andrelated components of a turbine engine;

FIG. 4 is an elevational view of exemplary baffle plates of an exemplaryinternal impingement cooling circuit with particulate matter built up onthe post-baffle side thereof;

FIG. 5 is an elevational view of the impingement cooled surfaces ofexemplary shrouds of an exemplary internal impingement cooling circuitwith particulate matter built up thereof;

FIG. 6 is a cross-sectional view of an exemplary embodiment of acleaning system and method according to the present disclosure installedin the internal impingement cooling circuit of FIG. 1;

FIG. 7 is an enlarged view of the exemplary cleaning system and methodof FIG. 6 during cleaning the internal impingement cooling circuit ofFIG. 1;

FIG. 8 is elevational view of the exemplary impingement cooled surfacesof the exemplary shrouds of FIG. 5 after an application of the exemplarycleaning system and method of FIG. 7;

FIG. 9 is an elevational view of the exemplary baffle plates of FIG. 4after an application of the exemplary cleaning system and method of FIG.7; and

FIG. 10 is a flow chart illustrating an exemplary method of cleaning aninternal impingement cooling circuit of a turbine engine according tothe present disclosure.

DETAILED DESCRIPTION

When introducing elements of various embodiments of the presentinvention, the articles “a,” “an,” “the,” and “said” are intended tomean that there are one or more of the elements. The terms “comprising,”“including,” and “having” are intended to be inclusive and mean thatthere may be additional elements other than the listed elements. Anyexamples of operating parameters are not exclusive of other parametersof the disclosed embodiments. Components, aspects, features,configurations, arrangements, uses and the like described, illustratedor otherwise disclosed herein with respect to any particular sealembodiment may similarly be applied to any other seal embodimentdisclosed herein.

Methods and systems according to the present disclosure provide for insitu uniform circumferential cleaning of the internal impingementcooling circuits of a turbine engine (i.e., cleaning around the fullcircumference of the turbine), without substantial disassembly of theengine, with detergent to remove matter therefrom to restore or improvethe cooling efficiency of the circuits, and thereby the performance ofthe turbine. For example, the methods and systems of cleaning internalimpingement cooling circuits of a turbine engine according to thepresent disclosure may be effective in returning the cooling features ofthe components that the internal impingement cooling circuits areconfigured to impingement cool to their original condition before entryinto service. The cleaning methods and systems according to the presentdisclosure may also provide for removal of matter from the components ofthe internal impingement cooling circuit and/or the components orsurfaces that the internal impingement cooling circuits are configuredto impingement cool that includes the most (or the most difficult toremove) matter deposited thereon so that the performance, lifespan orfunction of the component is substantially corrected or fully restored.For example, the methods and systems according to the present disclosuremay provide for cleaning the “dirtiest” impingement cooling circuit(such as the circuit including the “dirtiest” impingement cooledcomponent) of the circumferentially arranged impingement coolingcircuits to ensure that the entirety of the circumferentially arrangedimpingement cooling circuits are corrected or restored. Similarly, foreach individual impingement cooling circuit and/or for each componentthat the internal impingement cooling circuits are configured toimpingement cool, the methods and systems according to the presentdisclosure may provide for effective cleaning of the region of eachcircuit and/or cooled component that is the “dirtiest” so that theperformance, life span and/or function of even the worst area of thecircuit and/or cooled component is substantially corrected or restoredto an acceptable level for effective impingement cooling during use ofthe turbine.

The methods and systems of cleaning turbine internal impingement coolingcircuits according to the present disclosure may be configured to cleaninternal cooling passages of a gas turbine engine with detergent bydelivering the detergent through one or more access, ports or aperturein the outer wall of the turbine without substantial disassembly of theturbine engine. In some embodiments, the turbine internal impingementcooling circuit cleaning methods and systems may be configured todeliver cleaning detergent in passages of the impingement coolingcircuits that typically operate at air pressures of up to 1,000 psiduring normal or typical turbine engine service. The methods and systemsof cleaning turbine internal impingement cooling circuits according tothe present disclosure may utilize the baffle plate system of internalimpingement cooling circuits (i.e., baffle plates that are used in forimpingement cooling) to deliver detergent to components that the baffleplates are configured to cool to improve cleaning efficiency of thecomponents.

While the methods and systems of cleaning internal impingement coolingcircuits of a turbine engine according to the present disclosure aredescribed in detail below with respect to particular internalimpingement cooling circuits that are configured or designed toimpingement air cool particular components (e.g., shrouds), the internalimpingement cooling circuit cleaning methods and systems of the presentdisclosure may equally be applied to other impingement cooling circuitsconfigured to cool other components of a turbine engine that are (or maybe) impingement air cooled, such as nozzles, vanes, heat shields (suchas combustor heat shields), blades, splashplates, etc. Further, althoughthe methods and systems of cleaning turbine internal impingement coolingcircuits according to the present disclosure are described in detailbelow with respect to internal cooling passages of the high pressuresection or portion of a gas turbine engine, the cleaning methods andsystems may equally be applied to other sections or portions of turbineengines with impingement cooling.

As such, an internal impingement cooling circuit of a turbine enginethat is utilized to clean a turbine engine, as disclosed herein, may beany turbine cooling circuit that includes a pre-impingement bafflecavity or plenum, a baffle or baffle plate with at least one aperturetherethrough, and a post-baffle cavity that, collectively, areconfigured to impingement cool a component, surface or portion of theturbine engine, typically during operation of the turbine engine. Thepre-baffle cavity is arranged or positioned upstream of the impingementbaffle plate and is configured to feed cooling air or other materialthrough the at least one aperture in the baffle plate, and thepost-baffle cavity is arranged or positioned downstream of the baffleand proximate or adjacent to the impingement cooled component orsurface. The term baffle or baffle plate is used herein to refer to anycomponent, portion, surface or mechanism that includes at least oneaperture extending therethrough that acts to generate at least onediscrete cooling jet that impinges on a surface or component in thepost-baffle cavity of an internal impingement cooling circuit of aturbine engine to cool the surface or component. As such, the baffleplate discussed below with respect to FIGS. 1-9 (with an impingementcooled shroud) is only one exemplary baffle plate embodiment, and anyother component, portion, surface or mechanism that includes at leastone aperture extending therethrough that acts to generate at least onediscrete cooling jet that impinges on a surface or component in apost-baffle cavity of an internal impingement cooling circuit of aturbine engine maybe utilized in the cleaning methods and systemsdisclosed herein.

There are a wide range of geometries and configurations of substantiallyenclosed volumes that serve as pre-baffle and post-baffle cavities, aswell as components, portions, surfaces or mechanisms that act as abaffle plate, of differing internal impingement cooling circuit inturbines. Any arrangement of a pre-baffle cavity, at least one aperturethat generates a discrete cooling jet (referred to in general herein asa baffle plate), and a component or surface that is impingement cooledby the at least one discrete jet in the post-baffle cavity may beutilized by the methods and systems described herein to clean a turbine.In such cleaning methods and systems, detergent is introduced into orotherwise enters a pre-baffle cavity or plenum of at least one internalimpingement cooling circuit, and passes through the at least oneaperture in the baffle to clean material from a component or surface ofthe turbine, such as the component or surface that the at least oneinternal impingement cooling circuit typically or otherwise impingentcools.

In this way, the methods and systems of cleaning internal impingementcooling circuits of the present disclosure are configured to employ apre-existing impingement cooling configuration to establish suitabledetergent flow conditions that effectively and efficiently clean foreignmaterial from the full area of the impingement cooled surface orcomponent. Stated differently, effective and efficient cleaningaccording to the present disclosure is performed by “spraying” detergentthrough a pre-existing baffle plate that is used in a turbine engine forimpingement cooling to clean the impingement-cooled internal componentor surface of the turbine. The inventors have determined that thedetergent jets can be configured such that each cleaned surface orcomponent of the internal impingement cooling circuits is cleaneduniformly over the full area of the impingement cooled surface orcomponent. The inventors have also determined that in turbines thatinclude circumferentially arranged or positioned internal impingementcooling circuits, each of the cooling circuits around the fullcircumference of the engine can be cleaned uniformly (i.e., eachimpingement cooling circuit provides at least a minimum cleaningefficiency that is effective in removing foreign material from the fullarea of the impingement cooled surface or component).

A number of factors that affect the efficiency and effectiveness of themethods and systems of the present disclosure to clean foreign matterfrom the cooled components or surfaces of a turbine engine have beenrecognized. For example, the inventors have determined that the deliverypressure of the detergent in the pre-baffle cavity, the flow rate of thedetergent through the aperture(s) of the baffle plate, the number ofapertures in the baffle plate, the velocity of the detergent when itexits the baffle plate, the velocity of the detergent when it impactsthe matter on the cooled component or surface, and the shear stressgenerated in the matter by the detergent each affect the efficiency andeffectiveness of utilizing detergent and impingement cooling circuits toclean foreign matter from the cooled components or surfaces. The patternof apertures in baffle plates that include a plurality of apertures, forexample, has been determined to affect the distribution of the resultingdetergent jets on the cooled component or surface and how the jetsimpact the matter on the cooled component or surface. In fact, it hasbeen determined that the angle of impingement of a detergent jet is afactor in whether or not the jet generates an appropriate impact againstthe matter on the component or surface and thereby removes the mattertherefrom. The angle of the axis of the baffle apertures in typicalimpingement cooling circuits may be oriented normal to the surface orcomponent that is cooled (and therefore cleaned), or may be angled withrespect to the surface or component that is cooled (and thereforecleaned). For example, the angle of the axis of baffle apertures used inthe cleaning methods and systems disclosed herein may be within therange of about 30 degrees to about 90 degrees with respect to thesurface or component that is cooled (and therefore cleaned). As theaperture configuration of baffle plates in turbine engines is typicallyconfigured based on air cooling efficiency, the cleaning methods andsystems of the present disclosure provide for full and uniform cleaningutilizing such pre-existing cooling-designed apertures.

The methods and systems of cleaning turbine internal impingement coolingcircuits according to the present disclosure may be effective insubstantially removing foreign matter from the components in which thecooling circuits are configured or designed to impingement cool and/orcomponents or aspects of the cooling circuits themselves. The foreignmatter may be any matter, such as particulate matter, that is built up,introduced or produced on or in one or more component or surface of theturbine engine during use of the engine that decrease the efficiency ofthe turbine or otherwise interfere or degrade one or more function orcomponent of the turbine. In this way, the foreign matter cleaned by themethods and systems disclosed herein may be any matter that is depositedand/or produced on components or surfaces of the turbine after initialmanufacture of the turbine that interfere with the proper, designed orideal efficiency, function or lifespan of the turbine as a whole and/orone or more component or sub-system of the turbine. For example, theforeign matter cleaned by the methods and systems disclosed herein maybe dust, sand, dirt, debris or other foreign matter or pollutant that isingested or otherwise introduced into the engine and deposited oradhered onto one or more component or surface of an impingement coolingcircuit and/or a component or surface that the impingement coolingcircuit is configured or designed to cool. The foreign matter may alsoinclude matter that was introduced into the engine and that has beenreacted, treated or otherwise altered by the heat, pressure, etc. withinthe engine. The foreign matter is a combination of soluble and insolubledust species that have been ingested by a turbine engine and deposited(e.g., built up over time) on one or more component or surface of animpingement cooling circuit and/or a component or surface that theimpingement cooling circuit is configured to cool.

The methods and systems of cleaning turbine internal impingement coolingcircuits according to the present disclosure may utilize one or moredetergent including a reagent composition that is effective in removingmatter that may be deposited or formed on underlying components orsurfaces of turbine internal impingement cooling circuits (including theimpingement cooled components or surfaces themselves). For example, themethods and systems of cleaning turbine internal impingement coolingcircuits according to the present disclosure may utilize a detergentthat is effective in removing oxide-based, chloride-based,sulfate-based, and/or carbon-based constituents of CMAS-based reactionproducts, interstitial cement, and/or subsequent layers of accumulatedmineral dust from turbine components, such as a detergent disclosed inU.S. patent application Ser. 14/484,897, filed Sep. 12, 2014. Morespecifically, the methods and systems of cleaning turbine internalimpingement cooling circuits according to the present disclosure mayutilize a detergent including a reagent that selectively dissolves theconstituents of foreign material in internal cooling passages of aturbine engine. As used herein, “selectively dissolve” refers to anability of the detergent to be reactive with certain predeterminedmaterials, and to be substantially unreactive with materials other thanthe predetermined materials. Specifically, the term “selectivelydissolve” is used herein with respect to the cleaning detergent of thesystems and methods of the present disclosure to refer to a detergentwith a reagent composition that reacts with foreign matter on underlyingcomponents within a turbine engine to facilitate removal of reacted andunreacted foreign material from the underlying turbine components, butthat is substantially unreactive with the material used to form theunderlying turbine components to limit damage to them during removal ofthe foreign matter (i.e., during a cleaning operation).

In some embodiments, the detergent may include an acidic, water-basedcleaning reagent including one or more organic surfactant and corrosioninhibitor designed to selectively dissolve sulfate, chloride andcarbonate based species of matter on turbine components while beingsubstantially unreactive with the material forming the turbinecomponents, such as metallic turbine components. In some embodiments,the metallic components may consist of nickel alloys, cobalt basedalloys, and/or steels. The reagent composition of the detergent mayinclude water within a range between about 25 percent and about 70percent by volume of the reagent composition, an acidic component withina range between about 1 percent and about 50 percent by volume of thereagent composition, and an amine component within a range between about1 percent and 40 percent by volume of the reagent composition. Thedetergent may be formed, at least in part, by diluting the reagentcomposition with water up to a factor of 40. It is believed, withoutbeing bound by any particular theory, that the acidic component of thedetergent is a primary driver that facilitates selective dissolution ofthe oxide-based, chloride-based, sulfate-based, and carbon-basedconstituents of the foreign material. Exemplary acidic componentsinclude, but are not limited to, citric acid, glycolic acid, polyacrylic acid, and combinations thereof. It is also believed, withoutbeing bound by any particular theory, that the amine component of thedetergent acts as a surfactant that facilitates reducing the surfacetension between the cleaning solution and the foreign material.Exemplary amine components include, but are not limited to,monoisopropanol amine and triethanol amine.

Internal impingement cooling circuits or passages 10 of an exemplary gasturbine engine in which the cleaning methods and systems of the presentdisclosure may be employed are shown in FIGS. 1-5. The internalimpingement cooling circuits 10 may be positioned in a high pressuresection of the turbine engine. For example, as shown in FIG. 1 anexemplary internal impingement cooling circuit 10 may be proximate(e.g., extending at least partially about) at least one first stagenozzle 14 and at least one first stage blade 16 and configured toimpingement air cool at least one portion or surface 30 of at least onefirst stage shroud 18 associated with the at least one first stage blade16 (i.e., the at least one shroud 18 is the component in which theinternal impingement cooling circuit 10 is designed or configured tocool). As noted above however, the internal impingement cooling circuit10 is only exemplary and the present disclosure may equally apply toother impingement cooled components of a turbine engine (i.e.,components other than a first stage shroud 18) as recognized by one ofordinary skill in the art.

The internal impingement cooling circuit 10 may include, define or forman internal cooling passageway 12 for directing a flow of cooling air toat least one back side surface 30 of at least one impingement baffleplate 20 positioned adjacent the cooled component (i.e., the at leastone shroud 18), as shown in FIGS. 1 and 2. In this way, the internalcooling passageway 12 of the impingement cooling circuit 10 feeds air tothe baffle plate 20 that, ultimately, impinges air onto the backside 30of the shroud 18 to cool the shroud 18. The cooling passageway 12 mayextend generally in a forward-to-aft direction. The internal coolingpassageway 12 may be provided or formed between an outer or exteriorwall or casing 50 and an inner wall or casing 52 of the engine, as shownin FIG. 1. The outer wall 50 of the engine may thereby isolate orotherwise prevent the internal cooling passageway 12 from being accessedfrom the exterior of the engine. In this way, the outer wall 50 of theengine must be breached or otherwise “opened” to provide an aperture foraccess or a passageway into the internal cooling passageway 12. Theinner wall 52 may define or form, at least partially, a combustionpathway 54 extending from a fuel nozzle 56 that feeds fuel to the firststage of the engine (i.e., the first stage nozzles 14 and blades 16). Inthis way the cooling passageway 12 may extend at least partially about,along or exterior to the combustion pathway 54.

As shown in FIG. 2 and discussed above, the internal cooling passageway12 may feed or otherwise be in fluid communication with at least onebaffle plate 20 of the internal impingement cooling circuit 10. In someembodiments, the baffle plate 20 may be coupled to or held by at leastone hanger member 22 positioned proximate to a back side orexterior-facing surface 24 of the baffle plate 20. In some embodiments,the hanger member 22 may “hold” or otherwise be coupled to a pluralityof baffle plates 20. The hanger member 22 and the baffle plate 20 mayform a pre-baffle cavity, plenum or space 34 between the hanger member22 and the back side 24 of the baffle plate 20, as shown in FIG. 2. Thepre-baffle cavity 34 (and/or the internal cooling passageway 12) may besubstantially airtight such that the cooling air (fed by the internalcooling passageway 12) is pressurized in the pre-baffle cavity 34. Insome embodiments, the cooling air in the pre-baffle cavity 34 and/or theinternal cooling passageway 12, while the turbine engine is in service,may operate at pressures up to about 1,000 psi.

In order for the cooling air to feed into the pre-baffle cavity 34 fromthe internal cooling passageway 12, the hanger member 22 may include ordefine at least one aperture or passageway 42 extending through thehanger member 22 from the internal cooling passageway 12 to thepre-baffle cavity 34. In this way, the pre-baffle cavity 34 and theinternal cooling passageway 12 may be in fluid communication via the atleast one aperture 42. The at least one aperture 42 in the hanger member22 may be configured to provide a sufficient flow rate, pressure andother characteristics or conditions of cooling air in the pre-bafflecavity 34 such that the baffle plate 20 effectively impingement aircools at least one backside, cooling side or portion 30 of the at leastone shroud 18.

As shown in FIGS. 2 and 3, the baffle plate 20 may include at least one(such as a plurality or array) of aperture or passageway 28 extendingthrough the baffle plate 20 from the pre-baffle cavity 34 proximate tothe back side 24 to a post-baffle cavity 36 proximate a front side 26 ofthe baffle plate 20. The front side 26 of the baffle plate 20 maysubstantially oppose the back side 24 of the baffle plate 20. The frontside 26 of the baffle plate 20 may be proximate or adjacent to thesurface or portion 30 of the component 18 in which the internalimpingement cooling circuit 10 is designed or configured to impingementcool during service of the turbine engine. In this way the post-bafflecavity 36 may extend between the front side 26 of the baffle plate 20and the surface or portion 30 of the component 18 in which the internalimpingement cooling circuit 10 is designed or configured to impingementcool. As shown in FIGS. 1-5, the impingement cooling circuit 10 may bedesigned or configured to impingement cool at least one shroud 18, andtherefore the front side 26 of the baffle plate 20 (and the post-bafflecavity 36) is proximate or adjacent to a back side or portion 30 of theshroud 18 and otherwise configured such that cooling air passing throughthe plurality of apertures 28 of the baffle plate 20 into thepost-baffle cavity 36 is impinged onto the back side 30 of the shroud18. In this way, the plurality of apertures 28 in the baffle plate 20may effectuate cooling of at least a surface 30 of a component 18 in thepost-baffle cavity 36 by air impingement cooling to cool a component 18that needs to be, or benefits from being, cooled.

It is noted that the impingement cooling circuit 10 may be designed tooptimize or otherwise provide efficient, effective and/or above apre-determined minimum level of cooling to the components 18 that theimpingement cooling circuit 10 is designed to cool (e.g., at least oneshroud, nozzle, etc.). For example, the delivery pressure of the coolingair in the pre-baffle cavity 34, the flow rate of the cooling airthrough the baffle plate 20, the number, arrangement/pattern, size,angulation, shape, etc. of the apertures 28 in the baffle plate 20, thevelocity of the cooling air when it exits the back side 26 of the baffleplate 20 into the post-baffle cavity 36, the velocity of the cooling airwhen it impacts the surface or portion 30 of the impingement cooledcomponent(s) 18 in the post-baffle cavity 36 (e.g., the back side 30 ofat least one shroud 18), and the like may be designed to provide optimumimpingement cooling efficiency to the impingement cooled component(s)18.

As the methods and systems of cleaning turbine internal impingementcooling circuits according to the present disclosure utilize existingimpingement cooling circuits 10, the methods and systems may beconfigured to generate or establish suitable cleaning detergent flowgeometry, characteristics or other conditions over the full area orsurface 30 of the impingement cooled component 18 to clean dust, sand,debris 38 or other matter utilizing the impingement cooling circuits 10that are configured, designed or optimized primarily or solely forcooling. Stated differently, as existing impingement cooling circuits 10are designed based on air cooling efficiency, the methods and systems ofcleaning turbine internal impingement cooling circuits according to thepresent disclosure may be configured to utilize such designs orconfiguration for optimum cleaning. However, the impingement coolingcircuits 10 (including the baffle plates 20) of the methods and systemsof cleaning a turbine according to the present disclosure may includedesigning configuring and/or utilizing impingement cooling circuits 10(including the baffle plates 20) designed, configured or otherwisesuited to balance impingement cooling during turbine operation, andimpingement cleaning of the impingement cooled-component 18.

An impingement cooling circuit 10 configured, designed or optimizedprimarily or solely for cooling may include a baffle plate 20 with aback side 26 that is spaced within the range of about 0.05 inches toabout 0.5 inches from the adjacent or proximate surface 30 of theimpingement-cooled component 18. In contrast, an impingement coolingcircuit 10 configured, designed or optimized to balance impingementcooling and impingement cleaning of a turbine component may include abaffle plate 20 with a back side 26 that is spaced within the range ofabout 0.1 inches to about 0.25 inches from the adjacent or proximatesurface 30 of the impingement-cooled component 18.

As illustrated in the graphical representation of FIG. 3, a turbineengine typically includes a plurality of circumferentially arrangedinternal cooling circuits. Thus, the internal cooling circuit 10 shownin FIGS. 1 and 2 and described above represents one of numerous circuitsthat may be circumferentially arranged in a turbine. Thecircumferentially arranged internal cooling circuits 10 may thereby eachinclude a passageway 12 for the cooling air, at least one baffle plate20, and at least one component 18 air impingement cooled by the baffleplate 20. In this way, FIG. 3 graphically illustrates turbine enginewith circumferentially arranged internal cooling circuits 10 eachincluding a passageway 12 for the cooling air, a shroud hanger 22, apair of baffle plates 20, and at least one shroud 18 cooled by the pairof baffle plates 20. The pair of baffle plates 20 may be supported orcoupled to a hanger 20 such that a centerline or midline 21 of eachhanger 20 is substantially aligned with the junction of the pair ofbaffle plates 20.

As shown in FIGS. 4 and 5 and discussed above, during use of a turbineengine, dust, sand, dirt, debris or other foreign matter, pollutant ormatter 38 that is ingested or otherwise introduced into the engine maybe deposited, adhered or otherwise built up on the components of theinternal impingement cooling circuits 10 and/or the components 18 orsurfaces 30 that the impingement cooling circuits 10 are configured ordesigned to cool. As shown in FIG. 4, the front side 26 of the baffleplates 20 may include the built up matter 38 which may clog or otherwisenegatively affect the cooling efficiency of the baffle plates 20. Asshown in FIG. 4, depending upon the service time of the engine, thefront side 26 of the baffle plates 20 may be substantially covered oroverlaid with the built up matter 38, such as substantially completelycovered by the built up matter 38. As also shown in FIG. 4, at least oneaperture 28 of the baffle plates 20 may be partially or fully blocked,clogged or plugged with the built up matter 38. The methods and systemsof cleaning turbine internal impingement cooling circuits according tothe present disclosure, as described further below, may substantiallyremove such built up matter 38 on the front side 26 of the baffle plates20 and/or in the apertures 28 of the baffle plates 20 of the internalimpingement cooling circuits 10.

Similarly, as shown in FIG. 5, the back side or impingement cooledcomponents, surfaces or portions 26 of the shrouds 20 (i.e., theimpingement cooled components) may include the built up matter 38. Insome embodiment, the back side or impingement cooled surfaces orportions 26 of the shrouds 20 may include bumps or raised portions thatmay tend to trap or otherwise accept the built up matter 38, as shown inFIG. 5. As also as shown in FIG. 5, the built up matter 38 on theimpingement cooled surfaces or portions 26 of the cooled components 18(e.g., shrouds) may insulate the components 18 or otherwise negativelyaffect the cooling efficiency of the impingement cooling via the baffleplates 20. Depending upon the service time of the engine, cooledsurfaces or portions 26 of the cooled components 18 may be substantiallycovered or overlaid with the built up matter 38 as shown in FIG. 5, suchas substantially completely covered by the built up matter 38. Themethods and systems of cleaning turbine internal impingement coolingcircuits according to the present disclosure, as described furtherbelow, may substantially remove such built up matter 38 on the cooledsurfaces or portions 26 of the cooled components 18 of the internalimpingement cooling circuits 10.

FIGS. 6-10 illustrate methods and systems of cleaning turbine internalimpingement cooling circuits according to the present disclosure forremoval of the built up matter 38 on the cooled surfaces or portions 26of the cooled components 18 of internal impingement cooling circuits 10(as shown in FIG. 4) and/or the front side 26 of the baffle plates 20 ofinternal impingement cooling circuits 10 (as shown in FIG. 5) of turbineengines with detergent 64. The detergent 64 may be delivered to at leastone baffle plate 20 that is used for impingement cooling in the turbineengine (e.g., in a high pressure section of a gas turbine engine), asshown in FIGS. 6 and 7. For example, in some embodiments the systems andmethods are configured to introduce detergent 64 to a pre-baffle cavity34 or otherwise proximate to a back side 24 of at least one baffle plate20 of a turbine engine such that the detergent 64 passes through theapertures 28 in the baffle plate 20 and acts at least upon the component18 that the baffle plate 20 is configured to air cool to clean built upmatter 38 from the component 18.

Detergent 64 may be delivered to the pre-baffle cavity 34 or proximateto the back side 24 of at least one baffle plate 20 via a detergentdelivery mechanism 60, as shown in FIG. 6. The detergent deliverymechanism 60 may provide a passageway or other detergent transportationmechanism or vehicle at least partially through the turbine internalimpingement cooling circuits 10 to a pre-baffle cavity 34 or otherwiseproximate to a back side 24 of at least one baffle plate 20 of a turbineengine. The detergent delivery mechanism 60 may be flexible, bendable,adaptable or adjustable hose, tube or tube-like mechanism that can bepassed through one or more portions of the turbine engine and to apre-baffle cavity 34 or otherwise proximate to a back side 24 of atleast one baffle plate 20, and deliver detergent 64 thereto. Thedetergent delivery mechanism 60 may be configured to attach, mate orotherwise couple with the at least one aperture 62 in at least onehanger mechanism 22 from the internal cooling passageway 12 to providedetergent 64 to the at least one aperture 62 and, ultimately, to theassociated pre-baffle cavity 34 or otherwise proximate to a back side 24of at least one baffle plate 20.

The detergent delivery mechanism 60 may extend to at least onepre-baffle cavity 34 or otherwise proximate to a back side 24 of atleast one baffle plate 20 of an impingement cooling circuit 10 toprovide a flow of detergent 64 thereto by extending at least partiallythrough an internal cooling passageway 12 of the impingement coolingcircuit 10. The detergent delivery mechanism 60 may access the internalcooling passageway 12, or otherwise extend to or be configured toprovide detergent 64 to at least one baffle cavity 34 or proximate to aback side 24 of at least one baffle plate 20, by through an outer wallor case 50 of the engine. For example, as shown in FIG. 6, the detergentdelivery mechanism 60 may extend through the outer wall or case 50 ofthe engine, through or along an internal cooling passageway 12, and toat least one aperture 62 in a corresponding hanger mechanism 22.However, the detergent delivery mechanism 60 may extend through anaccess or aperture 66 in the outer wall or case 50 of the engine and toat least one baffle cavity 34 or proximate to a back side 24 of at leastone baffle plate 20 without passing through or into the internal coolingpassageway 12.

The detergent delivery mechanism 60 may transmit or provide detergent 64to the internal impingement cooling circuits 10 of a turbine enginethrough at least one aperture 66 in the outer wall or case 50 of theengine. In this way, the cleaning systems and methods of the presentdisclosure allow cleaning of the engine without removal of the enginefrom service and/or substantial disassembly of the engine to perform thecleaning. The at least one aperture 66 in the outer wall or case 50 ofthe engine utilized by the detergent delivery mechanism 60 transmit orprovide detergent 64 to at least one pre-baffle cavity 34 or otherwiseproximate to a back side 24 of at least one baffle plate 20 of animpingement cooling circuit 10, such as through an associated internalcooling passageway 12, may be an already existing access port in theouter wall 50 (i.e., a port that is utilized by the turbine engine for apurpose different than cleaning of the internal impingement coolingcircuits 10). For example, the at least one aperture 66 in the outerwall or case 50 of the engine that the delivery mechanism 60 passesthrough may be a bore scope access port, fuel nozzle port or flange,ignitor port, instrumentation access port or any other pre-existing portof the engine. At least one part or mechanism utilizing the port 66 ofthe engine may be removed such that the port 66 is exposed or otherwiseavailable to the delivery mechanism 60. For example, as shown in FIG. 6,at least a portion of a fuel nozzle may be removed from the respectiveaperture or port 66 in the outer wall 50 of the turbine engine and thedelivery mechanism 60 may extend through the “open” port 66 and into therespective internal cooling passageway 12 (and, ultimately, to therespective at least one baffle cavity 34 or proximate to a back side 24of at least one baffle plate 20. However, the at least one aperture 66in the outer wall or case 50 of the engine utilized by the deliverymechanism 60 to provide detergent 64 to at least one baffle plate 20 maybe an aperture 66 that is not pre-existing and/or that is for a purposedifferent other than cleaning of the internal impingement coolingcircuits 10.

With the detergent delivery mechanism 60 extending through the outerwall or case 50 of the engine and to at least one baffle cavity 34 orproximate to a back side 24 of at least one baffle plate 20 (such as byextending at least partially through an internal cooling passageway 12and to at least one aperture in an associated hanger mechanism 22),detergent 64 may be passed through or otherwise delivered by thedetergent delivery mechanism 60 to the baffle plate 20 such that thedetergent 64 passes through the apertures 28 in the baffle plate 20 intothe post-baffle cavity 36 and is impinged or otherwise physically actsat least upon the component 18 that the respective internal impingementcooling circuit 10 is configured to cool and that has become covered orincludes matter 38 that was deposited thereon during service. Thedetergent 64 that passes into the post-baffle cavity 36 may also actupon the front side 26 of the baffle plate 20 to remove matter 38 thatalso built up thereon. In this way, methods and systems of cleaningturbine internal impingement cooling circuits according to the presentdisclosure utilize baffle plates 20 to generate an array of detergentcleaning jets in the post-baffle cavity 36 when detergent 64 isdelivered to pre-baffle plenums/cavities 34 or otherwise proximate to aback side 24 of baffle plates 20 of an impingement cooling circuit 10 toclean matter 38 from at least the components 18 that the internalimpingement cooling circuits 10 are configured to cool.

To ensure such cleaning jets of detergent 64 are formed and areeffective in removing the matter 38 built up on at least the components18 that the internal impingement cooling circuits 10 are configured tocool (and, potentially, the front sides 26 of the baffle plates 20), thepressure, flow rate, temperature and other conditions or metrics of thedetergent 64 delivered by the detergent delivery mechanism 60 into thepost-baffle cavity 36 may be configured or controlled. For example, thedelivery mechanism 60 may be in fluid connection with a source ofdetergent 64 that feeds or otherwise provides the detergent 64 to thedetergent delivery mechanism 60. The detergent source 62 may regulate atleast one of the temperature and pressure of the detergent 64 deliveredby the delivery mechanism 60 to the baffle plenums/cavities 34 orotherwise proximate to the back sides 24 of the baffle plates 20 andinto the post-baffle cavity 36. Detergent 64 is delivered to the baffleplenums/cavities 34 or otherwise proximate to the back sides 24 of thebaffle plates 20 by the detergent source 62 and the detergent deliverymechanism 60 at pressures within the range of about 1 psi to about 1000psi to clean matter 38 in the post-baffle cavity 36 (e.g., thecomponents 18 that the internal impingement cooling circuits 10 areconfigured to cool and, potentially, the front side 26 of the baffleplates 20). However, detergent 64 may be delivered to the pre-baffleplenums/cavities 34 or otherwise proximate to the back sides 24 of thebaffle plates 20 by the detergent source 62 and the detergent deliverymechanism 60 at lower pressure such that the detergent 64 is asubstantially passive or stagnant fluid in the pre-baffle cavity 34 orotherwise proximate to the back side 24 of the baffle 20.

The effectiveness and/or efficiency of the jets of detergent 64 in thepost-baffle cavity 36 in cleaning matter 38 built up on the components18 that the internal impingement cooling circuits 10 are configured tocool (and, potentially, the front sides 26 of the baffle plates 20 ofthe internal impingement cooling circuits 10), characteristics ormetrics of the jets may play a role. For example, the angle of impact ofthe jets of detergent 64 in the post-baffle cavity 36 may be configuredto generate appropriate impact against the matter 38. Similarly, thedelivery very pressure and flow rate range of the detergent 64 into thepre-baffle plenums/cavities 34 or otherwise proximate to the back sides24 of the baffle plates 20 by the detergent source 62 and the detergentdelivery mechanism 60 may be configured to establish effective and/orefficient detergent jet geometry and pattern in the post-baffle cavities36. Other factors that may affect detergent 64 cleaning, and thereforemay be configured or considered in a particular cleaning operation orcleaning system configuration, may include the pattern of apertures 28in the baffle plate 20, the flow rate of the detergent 64 through thebaffle plate 20, the number of apertures 28 in the baffle plate 20, thevelocity of the detergent 64 when it exits the baffle plate 20 into thepost-baffle cavity 36, the velocity of the detergent 64 when it impactsthe matter 38, and the shear stress generated in the matter 38 by thedetergent 64. For example, the delivery pressure and flow rate range ofthe detergent 64 into the pre-baffle plenums/cavities 34 or otherwiseproximate to the back sides 24 of the baffle plates 20 by the detergentsource 62 and the detergent delivery mechanism 60 may be configured toestablish effective and/or efficient detergent jet geometry and patternin the post-baffle cavities 36 for one or more particular impingementcooling circuit 10 such that the matter 38 built up on at least eachimpingement cooled surface or component 18 is cleaned uniformly over thefull area thereof.

The methods and systems of cleaning turbine internal impingement coolingcircuits according to the present disclosure may also include passingmaterial other than the cleaning detergent 64 through the at least oneaperture 28 of the baffle plate(s) 20 such that it is impinged at leastupon the component or surface 18 that the baffle plate(s) is configuredto cool before and/or after utilizing the detergent 64. For example, themethods and systems of the present disclosure may include passing atleast one cycle of gases and/or liquids through the at least oneaperture 28 of the baffle plate(s) 20 such that it/they is/are impingedat least upon the component or surface 18 that the baffle plate(s) isconfigured to cool before and/or after utilizing the detergent 64. Forexample, the methods and systems of cleaning turbine internalimpingement cooling circuits according to the present disclosure mayinclude passing cycles of steam, detergent 64, and liquid water throughthe at least one apertures 28 of at least one baffle plate 20 such thatthey are each impinged at least upon the component or surface 18 thatthe at least one baffle plate is configured to cool.

The methods and systems of cleaning turbine internal impingement coolingcircuits according to the present disclosure may uniformly clean matter38 from circumferentially arranged internal impingement cooling circuits10, such as that illustrated in FIG. 3. The detergent delivery mechanism60 may extend proximate to each of the circumferentially arranged baffleplates 20 to provide detergent 64 thereto for impingement cleaning ofmatter 38 deposited on circumferentially arranged components 18. Forexample, the detergent delivery mechanism 60 may be configured tointroduce or provide detergent 64 to the pre-baffle cavity 34 orotherwise proximate to a back side 24 each of the circumferentiallyarranged baffle plates 20 of a turbine engine to effectuate uniformcleaning around the full circumference of the internal cooling passages10 of a turbine engine. The turbine engine may be mounted or otherwiseoriented with the propulsion shaft extending substantially vertically(such as during typical maintenance of turbine engines) and asubstantially equal amount of detergent 64 (or delivery pressure of thedetergent 64) may directed or introduced to the pre-baffle cavity 34 orotherwise proximate to a back side 24 each of the circumferentiallyarranged baffle plates 20 of the engine to substantially uniformly cleanmatter 38 from at least the components 18 that the internal impingementcooling circuits 10 of the engine are configured to impingement cool.The turbine engine may be mounted or otherwise oriented with thepropulsion shaft extending substantially horizontal (such as duringtypical operation of turbine engines) and the amount of detergent 64 (ordelivery pressure of the detergent 64) that is directed or introduced tothe pre-baffle cavity 34 or otherwise proximate to a back side 24 eachof the circumferentially arranged baffle plates 20 of the engine may beadjusted to compensate for gravity so as to effectuate similar detergentjet-component interactions around the full circumference of the engineto substantially uniformly clean matter 38 from at least the components18.

The end result of the methods and systems of cleaning turbine internalimpingement cooling circuits according to the present disclosure areshown in FIGS. 8 and 9. As shown in FIG. 8 as compared to FIG. 5, themethods and systems of cleaning turbine internal impingement coolingcircuits according to the present disclosure are effective in utilizingdetergent 64 to impingement clean and thereby remove matter 38 that hasbuilt up on the impingement cooled surfaces 30 of the components 18 thatthe baffle plates 20 of the internal impingement cooling circuits 10 areconfigured to impingement cool, such as impingement air cool. As shownin FIG. 8, the entirety of the impingement cooled surfaces 30 of thecooled components 18 may be substantially free of matter 38 after acleaning operation such that the impingement cooled surfaces 30 aresubstantially similar to their as-manufactured condition and initialcooling efficiency (at least with respect to the lack of matter 38thereon). Similarly, as shown in FIG. 9 as compared to FIG. 4, themethods and systems of cleaning turbine internal impingement coolingcircuits according to the present disclosure are effective in utilizingdetergent 64 to remove matter 38 that has built up on the front sides 26of the baffle plates 20 of the internal impingement cooling circuits 10that are configured to impingement cool, such as impingement air cool.As shown in FIG. 9, the entirety of the front sides 26 of the baffleplates 20 adjacent or proximate to the impingement cooled surfaces 30 ofthe cooled components 18 may be substantially free of matter 38 after acleaning operation such that the front sides 26 of the baffle plates 20are substantially similar to their as-manufactured condition and initialcooling efficiency (at least with respect to the lack of matter 38thereon).

As shown in FIG. 10, an exemplary method of cleaning turbine internalimpingement cooling circuits 170 according to the present disclosure mayinclude obtaining 172 a turbine engine including circumferentiallyarranged internal impingement cooling circuits. Each internalimpingement cooling circuit may include with a baffle plate configuredto air impingement cool a respective circumferentially arrangedcomponent of the turbine engine. Each baffle plate may include a backside, a front side positioned proximate to the respective impingementcooled component, and apertures extending from the front side to theback side. The method of cleaning turbine internal impingement coolingcircuits 170 may also include providing 174 an access to an internalcooling passageway of each of the circumferentially arranged internalimpingement cooling circuits through an outer wall of the turbineengine, as shown in FIG. 10. Providing 174 an access to an internalcooling passageway may include exposing or otherwise forming orproviding a port or aperture through the outer wall of the turbineengine. As also shown in FIG. 10, the method of cleaning turbineinternal impingement cooling circuits 170 may also include positioning176 a detergent delivery mechanism through the access in the outer wallof the turbine, into the internal cooling passageway, and proximate tothe back sides of the baffle plates. Positioning 176 a detergentdelivery mechanism proximate to the back sides of the baffle plates mayinclude positioning or arranging the detergent delivery mechanismproximate in fluid communication with a pre-baffle cavity associatedwith each baffle plate of each internal impingement cooling circuit,such as via an aperture in a hanger mechanism forming a pre-bafflecavity in concert with a respective baffle plate.

As also shown in FIG. 10, the method of cleaning turbine internalimpingement cooling circuits 170 may also include introducing 178detergent to a back side of at least one baffle plate of the turbineengine such that the detergent passes through apertures in the at leastone baffle plate and acts at least upon the at least one component thatthe at least one baffle plate is configured to air cool to clean matterfrom the at least one component. Introducing 178 the detergent may beaccomplished via the detergent delivery mechanism. Introducing 178detergent to a back side of at least one baffle plate of the turbineengine includes introducing the detergent such that the detergent passesthrough apertures in the at least one baffle plate and acts on the atleast one component that the at least one baffle plate is configured toair cool and the front side of the at least one baffle plate to cleanmatter therefrom. Cycles of steam, detergent, and liquid water may bepassed through the apertures in the at least one baffle plate andimpinged at least upon the at least one component that the at least onebaffle plate is configured to air cool to clean matter from the at leastone component.

EXAMPLES

The methods and systems of cleaning turbine internal impingement coolingcircuits, having been generally described, may be more readilyunderstood by reference to the following examples, which are includedmerely for purposes of illustration of certain aspects and embodiments,and are not intended to limit the methods and systems in any way.

In the examples, the methods and systems of cleaning turbine internalimpingement cooling circuits of the present disclosure were performed oninternal impingement cooling circuits of an aircraft turbine engine thatwere configured to impingement cool the high-pressure shrouds of theengine. The back side(s) or rear surface(s) of the shrouds weretherefore cooled by the impingement cooling air of the internalimpingement cooling circuits during normal operation of the engine. As aresult, particulate matter (such as dust and debris) was deposited orbuilt up on the back side(s) or rear surface(s) of the shrouds, therebysubstantially reducing the heat transfer effectiveness of theimpingement cooling circuits and leading to an undesirable increase inthe flow path surface temperature of the shrouds during use of theengine. As such, the example cooling methods and systems were performedto impingement clean the back side(s) or rear surface(s) of the shrouds,and the front sides of the baffle plates of the circuits, withdetergent.

Example 1

Tests of the delivery methods and system of the present disclosure wereperformed, in part, to analyze the effect of detergent flow rate ondetergent shroud wetting and, ultimately, shroud cleaning. The flowthrough the baffle was also analyzed tested to ensure sufficientpressure of the impingement fluid through the apertures in the baffleplate at the front side of the baffle plate, so that each jet in thearrangement was essentially normal to the surface of the shroud for allpositions around the full circumference of the circumferentiallyarranged shroud assembly in the engine.

The velocity of the impingement fluid through the shroud hangerapertures was about 1.3 m/s, and the velocity of the impingement fluidthrough the baffle apertures was about 0.4 m/s. In order to assess flowthrough the baffle plate apertures and the impingement of the detergentjets on the back side of the shroud, testing was performed with theshroud removed from the shroud hanger.

Wetting tests were also performed for shrouds attached to the shroudhanger in order to determine the uniformity of potential cleaning as afunction of orientation or position around the full circumference of theengine (i.e., circumferentially arranged cooling circuits coolingcircumferentially arranged shrouds). Specifically, shrouds at threepositions around the circumference of the engine, positioned at about 3o'clock, about 6 o'clock, and about 9 o'clock, were tested to determinethe effect of position or orientation on detergent flow (i.e.,simulating orientation of an engine oriented substantially horizontal).The shrouds were initially exposed separately to 4 detergent flow ratesof 400, 600, 800, and 1000 ml/minute for 30 seconds. Detergent flowrates as high as 2000 ml/minute were also explored. The dust ormatter-loaded surfaces of the shroud appeared darker when exposed to thedetergent. Detergent wetting was used as a gauge of the uniformity ofthe exposure of the dust or matter on the shroud surface to thedetergent during cleaning. The cleaning uniformity over each fullshroud, as well as uniformity of cleaning from shroud to shroud, wasanalyzed. It was determined therefrom that the 400 ml/minute flow ratewas needed to wet substantially all of the surface area of the shroudoriented at the 12 o'clock position, the 800 ml/minute flow rate wasneeded for the shroud positioned or oriented at the 6 o'clock position,and the 1000 ml/minute flow rate was needed for the shroud positioned ororiented at the 3 o'clock position.

A 30 second exposure of the 1000 ml/minute detergent flow rate was thentested on shrouds arranged or oriented for every clock position aroundthe circumference of the engine (i.e., simulating orientation of anengine oriented substantially horizontal). For the 30 second exposure ofthe fluid at the 1000 ml/minute detergent flow rate, it was determinedthat almost all the surface area of every shroud was wetted by thedetergent. The shrouds that showed the least wetting included those atthe 2 o'clock, 5 o'clock, 7 o'clock, and 10 o'clock positions. It wasnoted that an exposure time greater than the tested 30 second exposuretime would improve wetting uniformity about the circumference of theengine.

Example 2

Tests were also performed to assess the cleaning effectiveness of thedelivery methods and system of the present disclosure on an actualaircraft engine assembly.

A set of shrouds was removed from a wide-body aircraft engine that hadoperated for about 1000 cycles in environmental conditions thatcontained a relatively high concentration of airborne particulate, suchas PM10 values of greater than about 80 micro grams per cubic meter, forexample. The shrouds were then photographed, and assessed/measured forthe degree of degradation, including flow path condition, cooling holecondition/performance, and the degree of particulate matter on the backside or impingement cooled surface of the shrouds. The shrouds were thenre-assembled into the same engine position/configuration and the wholeshroud assembly in the circumferential shroud hanger assembly was thensubjected to a cleaning sequence of steam, detergent, and water, inorder to test removal of the particulate matter from the back-side orimpingement cooled surface of the shrouds.

Cleaning detergent was delivered to the hanger members, baffle platesand, ultimately, the shrouds utilizing the delivery method or system ofthe present disclosure in order to generate uniform cleaning of theshrouds around the full circumference of the turbine engine. Thedetergent was delivered to the apertures in the hanger members such thata flow rate of about 1000 ml/minute was provided to each shroud (i.e.,at the post-baffle cavity) for cleaning each shroud impingement cooledsurface at every position around the full circumference of the engine.For each hanger member there were two apertures for the specific enginethat was cleaned. Hence, the flow rate was about 500 ml/minute througheach hanger aperture. The flow conditions and flow rate delivered to theapertures of the shroud hanger members generated an arrangement of jetsthrough the baffle plates and into the post-baffle cavity.

More specifically, cleaning tests were performed using a series of steamand/or detergent cycles to form a full cleaning cycle. Superheated steamwas utilized through the system to pre-heat the part to be cleaned(i.e., the back side or impingement cooled surface of the shrouds), anddetergent was utilized through the system to selectively dissolve theoxide-based, chloride-based, sulfate-based, and carbon-basedconstituents of the foreign material built up on the shrouds.

A first sequence included an application of superheated steam at atemperature of about 105° C. for about 16 minutes. A second sequenceincluded an application of about 35-times diluted Citranox® at a flowrate of about 1000 mL/min for each shroud, at a temperature of greaterthan about 70° C. for a duration of about 5 minutes. After theapplication of Citranox®, an application of superheated steam attemperature of greater than about 105° C. for about 16 minutes wasutilized. A third sequence included an application of about 35-timesdiluted Citranox® at a flow rate of about 1000 mL/min for each shroud,at a temperature of about 80° C. for a duration of about 5 minutes, andan application of superheated steam at temperature of greater than about105° C. and for a duration of about 16 minutes. A fourth sequenceincluded an application of about 35-times diluted Citranox® at a flowrate of about 1000 mL/min for each shroud, at a temperature of greaterthan about 70° C. for a duration of about 5 minutes. A fourth sequenceincluded an application of water at a flow rate of about 1000 mL/min foreach shroud, at a temperature of about 20° C. for a duration of about 20minutes. As there were forty (40) total shrouds in the fullcircumferential engine assembly, the total flow rate of detergentdelivered to the engine to generate uniform circumferential cleaning wasabout 40,000 mL/min.

After completion of this full cleaning cycle, the shrouds were removedfrom the turbine engine and examined after drying. For example, thecondition of the shrouds were assessed and/or measured, including theflow path condition, cooling aperture condition/performance, and thedegree of particulate matter on the back side or impingement cooledsurface of the shrouds.

It was found that the cleaning system and method provided substantiallyuniform distribution of detergent over the whole rear or impingementcooled surface of the shrouds. It was also found that the cleaningsystem and method provided substantially uniform removal of dust, debrisor particulate matter on the impingement cooled surface using thecleaning sequence described below. For example, it was determined thatmore than about 85 percent by mass of the original dust or particulatematter had been removed from the shrouds, and there was uniform removalof the dust over the full surface of each shroud. It was therebyconcluded that the arrangement of detergent cleaning jets, the flow rateof detergent, and the cleaning cycles used to clean the shrouds withinthe engine had provided uniform cleaning of the shrouds. In addition, itwas determined that each shroud around the circumference of the enginewas cleaned to a similar degree of dust removal. Hence, is was concludedthat the arrangement of detergent cleaning jets, the flow rate ofdetergent, and the cleaning cycles used to clean the shrouds within theengine had provided uniform circumferential cleaning of thecircumferentially arranged impingent cooled surfaces or portions of theshrouds of the turbine engine.

It is to be understood that the above description is intended to beillustrative, and not restrictive. Numerous changes and modificationsmay be made herein by one of ordinary skill in the art without departingfrom the general spirit and scope of the inventions as defined by thefollowing claims and the equivalents thereof. For example, theabove-described embodiments (and/or aspects thereof) may be used incombination with each other. In addition, many modifications may be madeto adapt a particular situation or material to the teachings of thevarious embodiments without departing from their scope. While thedimensions and types of materials described herein are intended todefine the parameters of the various embodiments, they are by no meanslimiting and are merely exemplary. Many other embodiments will beapparent to those of skill in the art upon reviewing the abovedescription. The scope of the various embodiments should, therefore, bedetermined with reference to the appended claims, along with the fullscope of equivalents to which such claims are entitled. In the appendedclaims, the terms “including” and “in which” are used as theplain-English equivalents of the respective terms “comprising” and“wherein.” Moreover, in the following claims, the terms “first,”“second,” and “third,” etc. are used merely as labels, and are notintended to impose numerical requirements on their objects. Also, theterm “operably connected” is used herein to refer to both connectionsresulting from separate, distinct components being directly orindirectly coupled and components being integrally formed (i.e.,monolithic). Further, the limitations of the following claims are notwritten in means-plus-function format and are not intended to beinterpreted based on 35 U.S.C. § 112, sixth paragraph, unless and untilsuch claim limitations expressly use the phrase “means for” followed bya statement of function void of further structure. It is to beunderstood that not necessarily all such objects or advantages describedabove may be achieved in accordance with any particular embodiment.Thus, for example, those skilled in the art will recognize that thesystems and techniques described herein may be embodied or carried outin a manner that achieves or optimizes one advantage or group ofadvantages as taught herein without necessarily achieving other objectsor advantages as may be taught or suggested herein.

While the inventions have been described in detail in connection withonly a limited number of embodiments, it should be readily understoodthat the inventions are not limited to such disclosed embodiments.Rather, the inventions can be modified to incorporate any number ofvariations, alterations, substitutions or equivalent arrangements notheretofore described, but which are commensurate with the spirit andscope of the inventions. Additionally, while various embodiments of theinventions have been described, it is to be understood that aspects ofthe disclosure may include only some of the described embodiments.Accordingly, the inventions are not to be seen as limited by theforegoing description, but are only limited by the scope of the appendedclaims.

This written description uses examples to disclose the inventions,including the best mode, and also to enable any person skilled in theart to practice the inventions, including making and using any devicesor systems and performing any incorporated methods. The patentable scopeof the inventions are defined by the claims, and may include otherexamples that occur to those skilled in the art. Such other examples areintended to be within the scope of the claims if they have structuralelements that do not differ from the literal language of the claims, orif they include equivalent structural elements with insubstantialdifferences from the literal language of the claims.

We claim:
 1. A system for cleaning a turbine engine that includes aplurality of internal impingement cooling circuits each with an internalcooling passageway in communication with at least one baffle plate of aplurality of baffle plates, the at least one baffle plate configured toair cool a respective circumferentially arranged component of theturbine engine, the system comprising: a delivery mechanism extendingthrough an opening in the outer wall of the turbine and proximate to aback side of each baffle plate; and a source of a detergent configuredto deliver the detergent to the back side via the delivery mechanismsuch that delivered detergent passes through at least one aperture ineach of the plurality of baffle plates and acts upon the respectivecircumferentially arranged component and a front side of each of thebaffle plates to clean matter therefrom; and wherein the amount ofdetergent introduced to the back side of each baffle plate is adjustedto compensate for gravity and effectuate uniform detergent jet-componentinteractions around a circumference of the engine to uniformly cleanmatter therefrom.
 2. The system of claim 1, wherein thecircumferentially arranged component is a shroud coupled to a shroudhanger positioned at least partially on a back side of the shroud, theshroud hanger comprising a hanger aperture, wherein the deliverymechanism extends to the hanger aperture to deliver the detergent into apre-baffle cavity that is defined between the shroud hanger and the backside of each baffle plate.
 3. The system of claim 1, wherein thedelivery mechanism extends to a pre-baffle cavity that is proximate tothe back side, and wherein the cleaned matter is at least about 85% ofthe mass of a total mass of foulant previously present on thecircumferentially arranged component.
 4. The system of claim 1, whereinthe detergent includes an acidic, water-based reagent with an organicsurfactant and a corrosion inhibitor in fluid communication with thedelivery mechanism.
 5. The system of claim 1, further comprising aplurality of circumferentially arranged components, wherein the deliverymechanism delivers detergent to each circumferential location around theplurality of circumferentially arranged component in equal amounts. 6.The system of claim 1, wherein the delivery mechanism delivers detergentto each of a 12 o'clock position, a 3 o'clock position, a 6 o'clockposition, and a 9 o'clock position around the circumferentially arrangedcomponent, and wherein the amount of detergent delivered to the 12o'clock position is about 40% of the amount of detergent delivered toeach of the 3 o'clock position and the 9 o'clock position.
 7. The systemof claim 1, wherein the delivery mechanism delivers detergent to each ofa 12 o'clock position, a 3 o'clock position, a 6 o'clock position, and a9 o'clock position around the circumferentially arranged component, andwherein the amount of detergent delivered to the 6 o'clock position isabout 80% of the amount of detergent delivered to each of the 3 o'clockposition and the 9 o'clock position.
 8. The system of claim 1, whereinthe delivery mechanism delivers superheated steam to the back side ofeach of the baffle plates for about 16 minutes.
 9. The system of claim1, wherein the detergent delivery mechanism delivers detergent at atemperature of about 70° C. to the back side of each baffle plate forabout 5 minutes.
 10. The system of claim 9, wherein the detergent isdiluted such that there are about 35 parts water for each partdetergent.
 11. The system of claim 1, wherein the delivery mechanismdelivers water to the back side of each baffle plate for about 20minutes.
 12. A system for cleaning a turbine engine that includes aplurality of internal impingement cooling circuits each with an internalcooling passageway in communication with at least one baffle plate of aplurality of baffle plates, the at least one baffle plate configured toair cool a component of the turbine engine, the system comprising: adelivery mechanism extending through an opening in the outer wall of theturbine and proximate to a back side of each baffle plate; and a sourceof a detergent that delivers the detergent to the back side of each ofthe baffle plates via the delivery mechanism; wherein a spacing betweenthe baffle plate and the component of the turbine balances impingementcooling and impingement cleaning.
 13. The system of claim 12, whereinthe spacing between the baffle plate and the component of the turbine isat least 0.1 inches.
 14. The system of claim 13, wherein the spacingbetween the baffle plate and the component of the turbine is betweenabout 0.1 and 0.25 inches.
 15. The system of claim 14, wherein thecomponent of the turbine is a circumferentially arranged shroud.
 16. Thesystem of claim 15, wherein the turbine engine is attached to anaircraft.
 17. The system of claim 16, wherein the source of thedetergent includes an acidic, water-based reagent with an organicsurfactant and a corrosion inhibitor in fluid communication with thedetergent delivery mechanism.
 18. The system of claim 17, wherein thedelivery mechanism delivers superheated steam to the back side of eachbaffle plate for about 16 minutes.
 19. The system of claim 17, whereinthe delivery mechanism delivers detergent at a temperature of about 70°C. to the back side of each baffle plate for about 5 minutes, andwherein the detergent is diluted such that there are about 35 partswater for each part detergent.
 20. A method of cleaning a turbine enginethat includes a plurality of internal impingement cooling circuits, eachwith a baffle plate, the plurality of internal impingement coolingcircuits configured to air cool a respective circumferentially arrangedcomponent of the turbine engine, the method comprising: introducingdetergent to a back side of each baffle plate of the turbine engine suchthat the detergent passes through at least one aperture in each baffleplate and acts at least upon the circumferentially arranged componentthat the baffle plate is configured to air impingement cool to cleanmatter from the circumferentially arranged component; and adjusting theamount of detergent introduced to the back side of each baffle plate tocompensate for gravity and thereby effectuate uniform detergentjet-component interactions around a full circumference of the engine touniformly clean matter from the circumferentially arranged component,wherein introducing detergent further comprises introducing detergent toeach of a 12 o'clock position, a 3 o'clock position, a 6 o'clockposition, and a 9 o'clock position around the circumferentially arrangedcomponent, and wherein the amount of detergent introduced at a baffleplate at a 12 o'clock position is less than the amount of detergentintroduced at each of a baffle plate at a 3 o'clock position and abaffle plate at a 9 o'clock position.